Hinge structure



July 5, P. F. WHITE HINGE STRUCTURE Filed May ?4, 1956 2 Sheets-Sheet 1INVENTOR. l PHIL/P F. WHITE I v /)i I BY Q I I P. F. WHITE HINGESTRUCTURE July 5, 1960 2 Sheets-Sheet 2 Filed May 24, 1956 FIG. 5

INVENTOR.

PHIL IP 5 WHITE United States Patent 2,943,751; I HINGE momma Philip F.White, La Mesa, cane, assignor to General Dynamics Corporation (ConvairDivision),-'San Diego, Calif., a corporation of Delaware Filed May 24,1956, Sl. No. 587,134

a 'Claimst Cl, 217- 60) and other types of airplanes are equipped withradar I equipment which provides the pilot with advance warning offlight weather conditions; The radar antenna is normally: housedwithina'rado'rrie dfJnon-rnetallic material positioned-onthe no eorthefairplanebody to pr tivid'e for'optimum' operating efficiency, For,aerodynamic purposes, theradornelisq of generally hemisphericalconfigjuration blending with the contourof the airp'lane body. In.ordertthat convenient accessibilityb'e afiorded for maintenance andservicing ,of the antenna, it isidesirable to attach the radome to theairplane body through. a

single pointhinge suspension inprefe'rence to a detachable mountingarrangement which latter alternative involves additional time andhandling to accomplish the same end. i I I However, hingingiof ahemispherical shape to the air-' plane body presents aproblem sincethehinge must carry the weight of the radome and further res'ist torqueloads transmitted through the hinge from the radome into the airplanebody. Single point hinge suspension, in andof itselfiin connectionwithlarge diameter radome'sj is not, sufficiently adequate in'view ofthe length of the r'noment armas determined by' thediameterof'thejradome. Furthenwhen in openposition, external forces suchas strong winds blowing against the radome irripos e a severe strain 7on the hinge as well as. to the structiirefto' which the hinge isattached.

From the foregoing it will he readily appar nt that a single hingeadaptedgto" pivotally secure a radome a: an

airplane body requires force accepting means to satisfactorily relievestrain which may be imposed on the hinge.

" 1 It is, therefore, an object of the present inventionto provide novelstructure for use in connection with a hinged member which serves .tominimize strainexerted upon the hinge. v

Another object of thisinvention' is to provide a stabilizer deviceforahinged member through which device torque strains are transmitted fordistributionover a relatively large bearing area. I 5 I II Anotherobject of this invention is to provide in connection with a-device ofthe character above prop means adapted to support a hinged member inopen position relative to its supporting structure.-

Another object of this invention is to provide a torque I distributingstabilizer device for a hinged member which is simple in construction,eflicient in operation, durable,

eateatea- $195,196?) 7 2 and which satisfactorily serves the purpose forw ch it is intended. I I I Other objects and features of the presentinvention will be readily apparent to those skilled in the art' from thefollowing specification and appended. drawings wherein is illustrated apreferred form of the invention, and in which: V I

Figure 1 is a perspective view showing the present invention embodied inan airplane, with the radome of the airplane being shown in openposition and associated radar mechanism exposed; I

Figure 2 is a side elevational view of the hinge stabilizer assembly ofthe present invention located on the nose portion of an airplane whichis shown in dot and dash lines; 7 h

Figure 3 is a front elevational view of the assembly shown in Figure 2;I

Figure 4 is an enlarged transverse sectional view taken on the linelV-'-IV of Figure 2;

Figure 5 is a sectional view taken on the line V=V of Figure 4, and I IFigure 6 is a sectional view taken along the line of Figure 3. 7

Referring now to the drawings and particularly to I Figure 1 a hingestabilizer assembly 10, constructed in accordance with the presentinvention, is shown in en ative association with an airplane indicatedgenerally in the, drawings by the numeral 11. Assembly 10 is located [atthe nose section of the airplane, which nose [section includesa radome12, made of a material which perrnits the readylpassage of microwaveenergy. Rado'me 12 of generally hemispherical configuration and ispivotally mounted on the body 13 of the airplane at its "upper marginaledge by a usual double-leaf hinge 14 having one of its leaves secured tothe radome 12 and the other to the body 13 as by nuts and bolts or inany other conventional fashion. .,Positioned on a bulkhead 15 of body13and adapted to be enclosed by radome 12 are a usual radarantenna and itsassociated equipment indicated generally by the numeral 16.

Rigidly awed to airplane bulkhead 15, generally midway between thelocation of hinge 14, and the center of the bulkhead 15, are two bearingblock's17 and two hearing blocks 13 arranged in alignment in aplaneparallel to the planeofjhe longitudinal axis of the. airplane.

. As shown in Figure '3', the two bearingblocks 18 are located inwardlyof the bearing blocks "17/ Bearing blocks 17 and 18'serve to journal atorque, shaft 19 which is secured against longitudinal displacementrelative'tdthe bearing' blocks by'a pair of stop means 21 carried bytorqueshaft 19 adjacent opposed facesof the bearing blocks 18. As shownin Figure 6, stop'mearis 21 comprises 'a pair of generally semi-circularelements fiz fitted at opposite sides of torque shaft 19 and secured 'tothe torque shaft 19 by a bolt and nut assembly'ZS;

Carried by shaft-19 are two triangulartruss assemblies 2 1, eachassembly 24 formed of a pair of braces 25 and Zewhich extend fromconnections with torque shaft 19 I at their inner ends to join at anapex as at 27. The braces 25 and 26 are secured to each other at theV-shaped juncture of their outer extremities asby welding and aresecured to the torque shaft 19 as by welding, for common movementtherewith. As shown, in their connection to torque shaft 19, brace 25will'be located on one side of a bearing block 17 and brac'e 2 6 on theopposite side. At the V-shaped juncture 27 of each'of the trussassemblies 24 there is formed a slot 28 within whichfis I secured, as bywelding, a plate 29. Each of thep'air' jo'f plates 29 extends beyond theouter end of its truss "24 and projects into a space provided betweenapair of track-engaging or slide members 31, and each is pivotallyconnectedto its associated pair of members 31 by a bolt prevent loss ormisplacement thereof.

,propped in open position.

and nut 33 as shown in Figure 5,- suitable recesses 34 being provided inmembers 31 to accommodate the head of bolt 32 and the nut 33. Bolt 32and nut 33,

thus serve to hold a pair of slide members 31 in assembly and -topivotally connect a plate 29 to such assembly.

Carried on radome 12 transverse to torque shaft 13 are a pair oflaterally spaced-apart, parallel, elongated tracks 36; which tracks aresecured in chord-wise disposition to radome 12 by suitable brackets 37.Tracks 36, as shown in Figure '4, are of generally C-shape configurationin cross section and include a top Wall 3-8, side walls 39 and a pair ofinwardly directed flanges 41 with a space between the opposed ends ofthe latter through which space plate 29 extends. Contained within thearea-way defined by the walls of each of the tracks 36 aretheinterconnected slide members 31 which rest upon'and are adapted toride along an extended trackway formed by the inwardly directed flanges41. Flanges 41 are not continuous along the lengths of tracks 36 butterminate short of the inner ends thereof as at 4'2 (Figure 2) to permitthe ready insertion of assembled slide members 31 into the passageway ofsuch track s. Each of the tracks '36 is provided with opposed openings43 in side walls 39 thereof, which openings are adapted to register withaligned openings 44 in slide members 31 when radome 12 is moved to itsdesired open positlon. With openings 43 and 44 in registry a pin 45 maybe inserted therethrough to lock the slide members 31 to the track. Withslide members 31 locked in posit1on trusses 24 are secured againstfurther movement and serve as props to hold radome 12 in open position.As shown n FigureA, one end of pin 45 is formed into a loop as at 46 towhich one end of a chain 47 is attached,

the other end being fastened. to convenient structure .to

In the closed position of radome 12 it will be secured 4 minate inwardlyof the end of the tracks 36. When the slide members 31 are moved beyondthe inner ends of flanges 41 they are free to be withdrawn from withintracks 36. Thereafter, hinge 14 may be removed or disassembled todisconnect radome 12 from the airplane.

While certain preferred embodiments of the invention have beenspecifically disclosed, it is understood that the invention is notlimited thereto as many variations will be readily apparent to thoseskilled in the art and the invention is to be given its broadestpossible interpretation within theterms of the following claims.

What I claim is: V V

1. In combination, a supporting structure, a member hingedly mounted atone point on said structure, and means for maintaining said hingedmember in adjusted position relative to said structure, said meanscomprising a torque member, journal means for rotatively mounting saidtorque member on said supporting structure, a plurality of brace meanscarried by said torque member and movable therewith, stop means on saidtorque member in engagement with said journal means for restraininglongitudinal displacement of said torque member along its axis ofrotation, and a plurality of slidably mounted means carried by saidhinged member, each having a pivotal connection with a brace means andeach adapted to be restrained against movement relative to said hingedmember to hold said hinged member in adjusted position.

2.' In combination, a supporting structure, a cover member hingedlymounted at one point on said structure and swingably movable betweenopened and closed positions, and means for maintaining said cover memberin opened position, said means comprising a torque memagainstinadvertent opening 'by usual quick disconnect fasteners (not shown).When itis desired to gain access to the radar equipment 16 covered byradome 12, the

disconnect fasteners are actuated to release the connection of radome 12to aircraft bulkhead 15, whereupon the relationship of the-axis of hinge14 and the axis of torque shaft 19 carrying the braces 25 and 26 causesthe track engaging members 31 to slide within tracks 36 in the directionof hinge 14. When radome 12 is lifted to a position substantially ninetydegrees from its closed posit on, openings 44 in slide members 31'align-with openings 43 in track walls '39; whereupon pin 45 may beinserted to lock trusses 24 to radome 12 to hold the latter With the useof the arrangement hereinabove described hinge 14 will be laternallystabilized and be relieved of .torque loads which might tend to tear itloose while the radome 12 is being moved between its open and closedPOSIUOIIS or in the event that but one pair of slide members 31 islocked to its track and a pin 45, inadvertently or otherwise, notinserted into the other pair of slide members 31; Such loads, as theyoccur, will be accepted by the various brace members 25 and 26 and willbe equalized-by the torque shaft 19 transmitting loads from thebraces 25and 26 at one side of the radome to the braces 25 and 26 at the oppositeside of the radome. By

relieving hinge 14 of the stresses of torque loads, a hinge 'is employedwhich is relatively'light and, simple in construction, there beingnonecessity for a heavy construc- ,tion to assure structural integrity.

:member pivotally mounted at one point on said structure her, meansmounting said torque member on said supporting structure for rotativemovement, aplurality of br'acemeans carried at one of their'ends by saidtorque member and movable therewith, means on said torque ble members,means pivotally connecting the opposite ends of said brace'm'ea'ns tosaid slidable members, and means for locking said slidable members totheir support members to retain saidcover member in opened positlon.

3. In combination, a supporting structure, a cover for movement betweenopened and closed positions, and meansadapted to accommodate torqueloads which are applied to said cover member when in opened position andfor maintaining said covermember' in its opened position, said meanscomprising a torque member, jourjral means for mounting said torquemember on said supporting. structurefor rotatiye mQYement, a pluralityof brace'means carried at one of their ends bysaid torque member andmovable in common therewith, means carried by said torque member forengagingsaid journal means to restrain movement of said torque memberalong its axis of rotative movement, a plurality of track means mountedon said cover member, slidable means mounted for reciprocal movement onsaid track means, said slidable means being arranged for ready removalfrom saidtrack means, means for pivotally connecting the opposite endsof said brace means to said slidable means, and means for locking saidslidable means to its associated track to retain said cover member inopened position.

- 4. In combination, a supporting, structure, a cover 1 member pivotallymountedat one point on said structure for movement between opened andclosed positions, means adaptedto accommodate torque loads which areapplied to said covermember when in opened position and for maintainingsaid cover member in its opened position, said means comprising aplurality of elongated track members mounted on saidcover memberinspaced side-by- ,side relation, a torque shaft, journal means forrotatively movement of said torque shaft along its axis of rotation,

a track engaging member slid-ably positioned on each of said trackmembers and having a pivotal connection with a projecting end of a bracemember, and locking means for fixedly securing said'track engagingmembers at their associated track members to hold said cover member inopened position. q

5. Stabilizing means for a cover member which is pivotally connected bya hinge member at one point to a supporting structure formovementbetween opened and closed positions, said stabilizing meanscomprising a pair of elongated track members chordally mounted on saidcover member in laterally spaced relationship, one on each side of saidhinge member, a torque shaft extending transverse to said track membersand joumalled on said supporting structure for rotative movement, a pairof spaced-apart brace means rigidly afiixed at one of their ends to saidtorque shaft for common movement therewith and projecting outwardlytherefrom, means for restraining movement of said torque shaft relativeto said supporting structure along its axis of rotative movement, atrack engaging member on each of said track members mounted forreciprocal movement thereon, means pivotally connecting each of saidbrace means at its projecting end to one of said track engaging members,and means for locking said track engaging member to its associated trackmember to hold said cover member in its opened position.

6'. In combination, a cover member, hinge means for pivotally connectingsaid cover member at one point to supporting structure for movementbetween opened and closed positions, stabilizing means for said covermember in its opened position comprising a torque member journalled onsaid supporting structure for rotative movement, a pair of generallyV-shaped brace means having the ends of their leg portions fixedlysecured to said torque member for common movement therewith, means forrestraining movement of said torque member relative to said supportingstructure along its axis of rotative movement, a pair of elongated trackmembers mounted on said cover member in laterally spaced relationship,one on each side of said hinge member, a track engaging member slidablypositioned on each of said track members for reciprocal movementthereon, means pivotally connecting each of said V-shaped'brace membersat its apex to one of the track engaging members, and means for lockingsaid track engaging members against movement on said track members tohold said cover member in its opened position.

References Cited in the file of this patent UNITED STATES PATENTS1,325,377 Richards Dec. 16, 1919 1,766,197 Shepard June 24, 19301,986,307 Wagner Jan. 1, 1935 2,006,603 Nordmark et al. July 2, 19352,013,542 Nordmark Sept. 3, 1935 2,070,046 Gredell Feb. 9, 19372,323,279 Van Zelm June 29, 1943 2,441,913 Taylor May 18, 1948 2,674,420Johnson Apr. 6, 1954 FOREIGN PATENTS 572,804 Ireland Dec. 8, 1896

